DE2203870A1 - Auxiliary instrument for piloting an aircraft - Google Patents

Description

DR. MOLLER-BORe DlPL-PHYS. DR. MANITZ DIPL-CHEM. DR. DEUFEL

DIPL-ING. FINSTERWALD DIPL-ING. GRÄMKOW 2 2 O Ί 8 7 Ω

PATENT LAWYERS

Munich, * ⁷ ' ^JAN - ¹⁹⁷² We / Obd - S 2337

NATIONAL INDUSTRIAL AEROSPATIALE

37 vol. De Montmorency Paris 16, France

Auxiliary instrument for guiding plug-in items

The invention relates to an aid instrument for aircraft guidance and in particular a device which instructs the pilot in conditions analogous to those of visual flight figurative alarm signal and information for the one to be executed Measure delivers by utilizing the reflex capacities of peripheral vision.

A plug-in stuff pilot benefits during landing or take-off of this capacity, which enables him to

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Dr. Müller-Bor * Dr. Manitz ■ Dr. Deufel - Dlpl.-Ing. Flntterwald Dipl.-Ing. Qrimkow BrauMchwaio, Am BOrgerpark · · Munich 22, Roberi-Koch-StraB · 1 7 Slutlg «rt-Btd Ctnnttatt, MarkWraS · 3

Τ · Ι · ίοη (063 ») 73β · 7 Telephone WD 2939«. Τ · Ι · Χ 5-22080 mbpat Ttl # «on (0711) 867261

Bank: Zaniralkaa ·· l «y« K. Veikabankan. Munich, account number M2C PMtKJMOk: Munich »m

more or less conscious of the visual impressions in the dynamic To perceive the arrangement of the elements that represent the area around the slope. By looking straight ahead in the direction remains fixed in front of him, he nevertheless takes in his entire field of vision the dynamic elements of the representation of peripheral areas are true, which provide him with a sensory impression on the parafovea, i.e., on that part of the retina of the eye which surrounds the central zone of concentrated vision or the yellow spot.

Flight tests have shown that the pilot is instantly aware of any peripheral vision irregularity, namely even before he realizes what is really happening. This is due to the fact that the visual reference marks a change with respect to a stable one signal characteristic state as it corresponds to the situation of the given flight, whereby the stable arrangement is recognized, through the pilot's experience, before a change occurs, as long as a normal situation is present. It thus let beneficial to a change in terms of to achieve a stable arrangement which immediately attracts the pilot's attention under conditions of the Instrument flight during aircraft guidance with no visibility (PSV) or in poor visibility, and information is therefore available, which has certain advantageous properties of visual flight.

There are aircraft pilot facilities known, which are arranged above the instrument panel or to the side of the instruments, which require the peripheral perception in that a displacement of a geometrical figure takes place, for example a helix or a network of oblique lines running in one direction or an opposite direction in response to a Command signal progresses. This command signal translates into

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one or the other direction the algebraic difference between a value of a parameter of the aircraft control, which is predetermined or normal, and a real value of this parameter.

In any case, it is the cylinder, the disk or the band that carry the geometrical figure that is found in one or the other shifted other direction, then immobile in the case in which the command signal is not present, namely if the aircraft flies in normal flight condition. Technically, the response to the command signal is thus more or less Immediate activation of a mechanical organ causes, with reversal of the direction of movement around the neutral location. Such control conditions generally make it possible not to ensure an instant and reliable display, and on the other hand, in the event of a malfunction of the System a curtain the observation window of the geometric Cover figures.

The invention thus provides a configuration which is based on a normally driven moving part is drawn, which rotates in the peripheral field of view of the pilot, the Rotational speed of the movable part is influenced in response to a command signal, part of the configuration is chosen so that it is partially invisible on the driven movable element when it is with his running at normal speed, namely through the stroboscopic Continuous effect of the retina, while this part reappears when the speed as a function of the impact a deviation signal decreases when the aircraft leaves the intended path, for example, to consequently the To make pilots aware of conditions that are analogous to those of visual flight.

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The invention is explained below, for example, with reference to the drawing described; in this shows:

Figure 1 shows a device according to the invention, Figure 2 is a section along II-II of Figure 1,

FIG. 3 shows a representation analogous to FIG. 1 in the normal operating state,

FIG. 4 shows an embodiment of FIG. 3 when a command signal occurs,

FIG. 5 shows an analogous view of an embodiment variant of FIG. 4, FIG. 6 shows a detailed view of a structural arrangement and

FIG. 7 shows a schematic representation of the arrangement of an aircraft cockpit equipment.

In Figures 1 and 2, an on-board instrument 10 is shown which has two drums 1 and 2 which, for example, have a diameter of D = 10 cm and a width of E = 3 cm.

The drums 1 and 2 are independent of each other on two motor devices arranged, which are indicated schematically at 3 and 4, are still centered on a common axis x-y, and they are driven by the individual motors (not shown).

A checkered configuration of dark color on a light background can be seen on the cylindrical outer surfaces of drums 1 and 2, which, for example, has lines 5 that run parallel to the axis of rotation x-y along the generatrix of the cylinder

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run and circles 6 that are perpendicular to the lines 5.

When the motors are switched off, the drums, which are from the Pilots in the direction of arrow f-. be seen a plaid Pattern (5f6), which differs from the light background according to the representation in Figure 1 is dark.

According to the invention it is provided that, in a normal flying condition, drums 1 and 2 are set in rotation every two, for example in opposite directions to one another, namely drum 1 in the direction of arrow f ₂ and drum 2 in opposite directions, the speed being such is chosen that the lines 5 are invisible to the retina of an observer by the stroboscopic effect by the rotation of the drums, while the network of circles 6, which lie in planes perpendicular to the axis of rotation xy, if they have a sufficient line thickness or a sufficient Have point markings, are only accessible to peripheral vision and represent an excellent stimulus for peripheral vision, specifically for normal jj'lugzuatände.

FIG. 6 shows a control arrangement of the device 10 according to of the invention, namely on two motors 7 and 8. These motors each drive a ring gear 9 and 11, respectively, in opposite directions Direction which are in engagement with the ring gears 12 and 13 on the short shafts 3 and 4.

The motors 7 and 8 are via two transmission lines 14 and 15 fed via two voltage converters 16 and 17.

In a normal situation, the motors 7 and 8, as already explained above, rotate in opposite directions to one another, and its speed is dimensioned as it is necessary to achieve the intended stroboscopic effect, according to which the pilot only uses the immovable

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Chen circular lines 6 perceives.

A computer represented by the block diagram 18 compares the predetermined size with the current value of the flight parameter, for which the device 10 supplies visual information relating to the action to be performed, for example to cancel a deviation with respect to a radio beam in the course of the approach to a landing area. The computer 18 possibly gives to the amplifier 19 over the line 20 a signal of the deviation between the specified value and the current value, which has the consequence that over the line 21 a command signal is given, which the speed of the motor 7 is slowed down via a voltage converter 16. Of the Motor 7 rotates the surface part of the drum in the direction of the Arrow f., Where the slowing down, which is triggered by the signal of the deviation, has the effect that the normal Speed invisible lines 5 reappear and then under the pilot's eyes in the direction of the Arrow f. (See Figure 4), at a speed which is, for example, inversely proportional to the amplitude of the action required to be performed.

Even if the line 22 introduces a signal "to rear up" in the transducer 17, the change in voltage has the effect that the motor 8 is slowed down and consequently the drum 2 is also slowed down, which is in the direction of the arrow f, rotates. Due to this slowdown, the lines 5 of the checkered pattern reappear and pass under the pilot's eyes in the direction of the arrow I _x - at a speed which is inversely proportional to the amplitude required for the movement to "das Rise up "to correct.

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If the device is to monitor the azimuth angle of the aircraft in relation to the runway, embodiment 110 of FIG. 5 according to the invention is advantageously used ₇ rotates has sufficient speed that the lines 105 of the checkered pattern can no longer be seen by the pilot, a progressive deceleration being provided by the intervention of a command computer which determines the difference between two data, namely between the azimuth the axis of the runway and the current azimuth, in such a way that the lines 105 again appear advancing, _{running in the direction of the arrow f Q} , thereby indicating to the pilot that he must come to the right.

Similarly, when the drum 102 slows down, it indicates that it must come to the left.

In FIG. 7, the on-board instrument panel 23 is shown what the classic instruments of aircraft control are, and the windshield 24. The lateral movement indicator 110 and the two indicators 10 for movements in altitude are arranged in the area of the pilot's peripheral vision. Command computers like 18 are suitably connected to amplifier 19 and transmit, according to the invention, the signals indicating which action is to be carried out, namely through suitable transmission lines 25 »to the instruments 10 and 110 of the first pilot, with a Doubling to the Oo pilot position shown at 26 is possible is.

Regardless of the displays, which for him from the careful reading of the scales on the instrument panel 23 or from the examination deriving from external natural reference points is that

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Pilot with his head held high, the yeast effect of the stimulus of the exposed to parafoveal vision, namely the displays 10 and 11 ü, which show the reaction effect in lateral and horizontal direction concern.

With the inventive device is for the pilot who according to instruments flies, the process of Iieflexaufnähme and The interpretation is therefore very similar to the process as it is to the Siohtflug is peculiar.

Ks mainly "when weak or not present at all The following processes are facilitated:

Manual approach and landing,

the monitoring of these phases with automatic plug,

the fetching (automatic or not),

starting and

The transition to manual control if the automatic system is a result of one Has been switched off in an accident or for any other reason.

The two 'pious' can also be separated into two different ones Axles be mounted, and the stroboscopic ^. » liffe ,, ktes variable configuration can be applied to the flat surface be drawn on a disc.

- patent claims -

0 Li ΰ: u / o 1 1 ε

Claims (1)

Pa ben t; ana ρrUohe In the tr union b der irlugZeuigiMihrung, daduroh geke η η ae L ο h η π t; , that dl0 deviation between a given throw and a momentary one, / erb in a windler (Ib ') of the speed a »in Ro bat ion bet'inaL icjnan. Ürgarui (I) is entered in the form of an iK »f'tjhlasLgnaLa (21) de rar f. That the v '/ inkelgeijoh Speed of theea organ (|) reduce WLrd, duü the Ober-L'üiohe dieaea Organa an overflowing conflguratLon (5, 6) aufv; eiüb, waLche et) acted, in the case of the original wind speed envisaged in the deviation b of the deviation to achieve a tropoakopisohen i, t'i. "Ect and that by other clear winds in • ioaction on the deviating century Another KonL'igurabion is presented to the PlLotmi u'lugiuujtände aniuiaoigen, which were reproduced on the Ina dream, and ^ only in an analogous Wo lye to the 3io htt Lug, liifjbrument naoh jinapruoh I, duduruh g υ ke η η ζ ei ο h η α t, daü wenLguten »t ', wei L'r-.haiiieLn (| and 2) yorgean 3ind, which are opposite to each other in continuous gold ujnL'oi · --shaped rotation are varaetac, by two motors ( '/ and M), DAT each motor in operation by an independent About Bra- ^ iUMf ₁ U line gea ρ eist isu that .v <ü terhiri a means for changing the Each speed ( ] 6 or IY ) is provided with a double input. Lab whose door input receives a command (.21 or 22) from a computer that is issued in response to a deviation that occurs between relative advertising between the parameters of the aircraft control and the second wingang U4 or 1 ¹ O Hpeiaung receives Onea Motora which iat intended to ernalten a certain niiisLmale normalu v / inkölgeuchwindigkeib -l'rommei upright, DAT each iTommel (.1 and 2) on its cylindrical Umfarigsf laugh a configuration awkward who have a Kon eras b 2098 JA / 01 16 BATH ORIGINAL daruhüLlt ( ^l j, 6), the α ο selected list, that the normal UeachwindigkeLC tunon to ι: U; r configuration (/.>) for the exercise of a Heobachtora LUiJt do not enter into ht'iuiliyinung, that a Ln command- ., which «from uu.u Ueohrif.it. · Lm u'al Le unites · Anomalous, i 'Ln der hrun ^ _; iu;) ^ titiand t will, Lu d «n era ten i ', ingang. ^ 1) deu _t VandL ^: .jra aLngoapti ia ι» will and a L; h Lu der , in β acts that the', yinkülgeucti /; Lud L-; ke ι t der. γοπηικ.ί (I) decreases to the under normal l) ediiu; iin; j, tjn urm i ;; ti. um an ; üii I ₁ >, ύ ·. \ ι · r.oiii ι _; ; ur'u-LLon wLeder Ln i'iratiheinunt ¹ , treben i: a Laanyn, au ilaß aiii. "dieae // eLao die au korr igLorondu abortuaLe ciLtuui. ion for dan PiLo ben aLiilii.bar has become Lat, and κ λ ar uni-ür lied Ladungen daa p & riphe run parafoveaLen iiohfm.i, Ina t L'ument after Anaprucjh ?., Daduruh g υ k υ η η aei ι; ti - · net that the contradictory confLgurabLon has an nviii-.it : -, from IiLnLuU (/)) to // ei; Jt, which is in the iViiaeubLLcih-m ent Lan; ¹ , from ,, ν- dea i'yLLndera vorLaufou and a /.,ve i tot »fieba '/ on in (6) buaii.-t, who advised the Liiiiyn dea eraben; u; j .junk-Vöt'Laufan that the LinLon {' }) doa era ten üotaea biii der nurmaLen urehgoucuv / Lndi-.icoL t der Lt-ommel {]) una lern t.bur α in.l and again Ln jiiracihein enter, // 'üiti dit *. α .r; ifi; h // indi-JcoL t in iieakbLon on ο in tJoftjtiLaa ignal (, L'O) only Korrtii-itur fiitisr Xb- Wfjiutiung decreases, ■ \, Lnutlösungen naoti Anap.-uiti], dadurcjr. ge Ic ■.) a i. . ', ·; \ a ti ■■ -neb that the practice (f4 or t '")), in which door the eye dea t'iloben the lines (5) , which end outside the pitcher the uromrnuL 1,1) geaoLchnaC a Charged when DIEA <; again in fcracheinun, ", please, ao i.ac selected such that the c, Ln weLctiüC * tan κ directly the tang auggei'Lerb wLrd: ι ae iviaßnahine required iat who meet au 13t in order to remove the ano ^ ulie daa elugaua oandea au and thus daa Abwyicü ..: .ίκ> ignai (2U). 2ÜUB34 / 0M6 .. 11 _ ^ 2 (J 3 8 7 f ι 5. 1 η a tr to ent i'ür PuV-MUg according to claim 1, characterized in that each jrommeJmotor (7 or 8) by a voltage converter (16 or 17) with two inputs is suitable, the first input (14 or 13) is used for feeding in the normal range and its second input (21 or 22) is branched off from the command circuit (20) of an amplifier (19) for the deviation signal or a jjefehlsrechner (10). 6. Instrument for the PSV-l ^il Hug after claim ^r 5, characterized ge Ii e η η ζ e 3 ο Ji η et that the] 3efehlaschaltung (2u) a Uignal in .Reaktion to a deviation between a given and a momentary one work abJbt. 7. Instrument for the PSV flight according to claim [? » characterized in that the command circuit (20) is on Signal in response to the deviation with respect to a spark sends out a beam of fire. 8. Instrument for the PSV flight according to AnsprucJi 1, characterized in that the configuration for the stroboscopic The effect on a licJieibe is gezc-icJinet. 20H03 /, / 01